固体火箭发动机用承压式爆炸箔点火器的设计与性能研究
Design and Performance Study of a Pressure-Resistant Exploding Foil Igniter for Solid Propellant Rocket Engine
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摘要:为确保固体火箭发动机点火过程的高安全性及点火后的密封承压性能，基于集成爆炸箔芯片与“冲击-爆轰-爆燃”传火序列，设计了满足30 MPa承压指标的爆炸箔点火器，并采用玻璃烧结、金线键合、集成装配及整体灌封工艺制备了样品。开展了爆炸箔点火器的典型环境适应性试验，并对试验后样品的冲击发火性能、密封承压性能进行了测试及表征。研究结果表明：环境试验前后电性能基本保持稳定，试验后样品输出峰值压强为8.6 MPa，发火延迟时间为6.4 ms，满足发动机可靠点火要求；成功与直列式电源、点火药盒进行了发火-点火联合匹配试验，验证了冲击发火性能；作用后爆炸箔点火器的密封承压性能满足30 MPa/60 s的发动机工作压强要求。
Abstract:To ensure high-safety ignition and sealed pressure-resistance performance after ignition in solid propellant rocket engine, an exploding foil igniter (EFI) with 30 MPa pressure-resistance specification was designed based on integrated exploding foil chip and the "shock-detonation-deflagration" low explosive train. Samples were prepared using glass sintering, gold wire bonding, integrated assembly, and overall potting processes. The typical environmental adaptability tests on the EFI samples were conducted, then the shock firing performance and sealing pressure performance after tests were evaluated. The results show that the electrical properties remain basically stable before and after the environmental tests, the peak output pressure is 8.6 MPa with a firing delay of 6.4 ms, meeting the engine's reliable ignition requirements. The joint firing-ignition matching experiments were also successfully performed with an in-line power supply and an ignition cartridge, verifying the shock firing performance. The sealing pressure performance of the EFI after tests can meet the engine's working pressure requirement of 30 MPa/60 s.
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